Experimental Analysis of the Interaction Between Rim Seal and Main Annulus Flow in a Low Pressure Two Stage Axial Turbine

Schrewe, Sebastian; Werschnik, Holger; Schiffer, Heinz-Peter

doi:10.1115/1.4023015

Cited by 32 publications

(12 citation statements)

References 15 publications

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“…Accordingly, the hot streak is distorted, but its spatial extent does not increase significantly across the vane row. Flow tracing has been applied by Schrewe [10], Feiereisen et al [11] and Lefrancois et al [12] to study the propagation of purge flow in low pressure turbines. The results of the last-mentioned working group have been identified to be transferable to engine conditions (Boutet-Blais et al [13]).…”

Section: Tracing Of Turbomachinery Flowsmentioning

confidence: 99%

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Werschnik

Schneider

Herrmann

et al. 2017

IJTPP

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The aerothermal interaction of the combustor exit flow on the first vane row has been examined at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt (Darmstadt, Germany). A baseline configuration of axial inflow and a variation of swirling combustor inflow have been studied. The nozzle guide vane (NGV) featured endwall cooling, airfoil film cooling and a trailing edge slot ejection as well as NGV-rotor wheel space purge flow. CO 2 is injected for coolant flow tracing. The results are compared to five hole probe (5HP) measurements. The experiments for the baseline configuration are accompanied by numerical simulations using a passive scalar tracking method to validate the results and study the propagation of the coolant flow. The endwall coolant injection is detected to influence the pressure losses in the NGV. It has an impact on the Trailing Edge (TE) coolant ejection as well. For swirling combustor inflow, increased NGV pressure losses and increased mixing of Rear Inner Discharge Nozzle (RIDN) coolant and main flow is observed. An influence of the clocking position of the swirler to the vane is detected. Additional losses within the NGV row can be assigned to the swirler by means of flow tracing.

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Section: Tracing Of Turbomachinery Flowsmentioning

confidence: 99%

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Werschnik

Schneider

Herrmann

et al. 2017

IJTPP

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“…Moreover, the blockage effects of the swirled and non-swirled rim seal flows were similar, because the blockage effect was primarily a function of the rim seal flow rate. Schrewe et al 13 performed experimental analysis of the interaction between rim seal and main annulus flow in a low pressure two-stage axial turbine, and reported that the rim seal flow blockage led the mainstream between the hub and 20% span to decelerate and the mainstream between the 20% span and 90% span to accelerate. Jia and Liu 14 numerically investigated the effect of rim seal and pointed out that the rim seal flow induced the blockage effect which would decelerate the flow near the hub and accelerate the mainstream at high spanwise position.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of the blockage effect caused by rim seal flow

Fan

Wang

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Blockage effect caused by the rim seal flow is one of the most important sources of loss in the interaction between the turbine rim seal flow and mainstream and has not been investigated in detail. To research the blockage effect, numerical simulations were presented for different rim seal flow rates. The pressure distribution was investigated and losses resulting from the blockage effect were analyzed. In addition, the influences of swirl ratio, inclination angle, and width were revealed. Results show that the blockage effect originates from the pushing and compression of egress flow to the mainstream and results in local pressure increase. The egress flow mainly blocks the mainstream downstream of the stator suction side and above the egress flow. Furthermore, the blockage effect strengthens with the increase of rim seal flow rate and weakens with the increase of swirl ratio. The effect of inclination angle and width on the blockage effect could be neglected. With the increase of rim seal flow rate, the blockage on the stator suction side causes the secondary losses to be reduced and the increasing expansion in the rotor passage leads to more losses at the tip and surface. A loss isolation method that defines the space region of loss in the rotor domain is established and proven to be effective. On an average, relative to the design condition, the overall loss introduced by the blockage effect increases by about 89.44% per 1% increase in the rim seal flow rate.

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“…McLean et al [17] investigated the injection effect of purge flow on the aerodynamic performance in a turbine, which found that velocity profile modification was related to the purge flow. Schrewe et al [18] performed an efficiency measurement and found an efficiency drop with the increase of rim seal mass flow rate in a two-stage low-pressure turbine. Zerobin et al [19,20] investigated the influence of four individual purge flows on the aerodynamic performance of turbine center frames with a 1.5-stage turbine test setup.…”

Section: Introductionmentioning

confidence: 99%

Particle Image Velocimetry (PIV) Investigation of Blade and Purge Flow Impacts on Inter-Stage Flow Field in a Research Turbine

Zhang

2019

Energies

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Flow field in the inter-stage is of great importance to jet engine turbine performance and efficiency. Investigation of flow fields is limited by the complex geometrical structure. Traditional measurement techniques, such as hot wire, pressure probe and laser Doppler velocimetry (LDV) can hardly obtain a planar information of the flow field simultaneously. To overcome this difficulty, an instantaneous planar velocimetry technique, the particle image velocimetry (PIV) technique is widely employed. However, there is no publication that studied the detailed flow field by PIV in a turbine inter-stage with the consideration of the influence of rotor blade and purge flow. This paper presents a quasi-three dimensional perspective of flow field between inlet guide vane (IGV) and rotor blade in a research turbine inter-stage by using a 2D PIV system. Coherent structures in the flow field are extracted by the proper orthogonal decomposition (POD) method. Time-averaged results show the ellipsoid structures caused by secondary flow in the inter-stage. Rotor blade influence to axial and radial flow is evaluated by time-averaged data and the first order POD mode. Egress of purge flow (9.4% of main annulus flow rate) leads to a domain with 60% axial velocity loss near hub and a growth over three times in radial velocity. POD analysis of purge flow shows detailed flow migration in the whole measurement plane.

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Experimental Analysis of the Interaction Between Rim Seal and Main Annulus Flow in a Low Pressure Two Stage Axial Turbine

Cited by 32 publications

References 15 publications

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

The Influence of Combustor Swirl on Pressure Losses and the Propagation of Coolant Flows at the Large Scale Turbine Rig (LSTR): Experimental and Numerical Investigation

Numerical investigation of the blockage effect caused by rim seal flow

Particle Image Velocimetry (PIV) Investigation of Blade and Purge Flow Impacts on Inter-Stage Flow Field in a Research Turbine

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